A rapid-rotation missile body structure and a rotation speed design method

Abstract

The application discloses a rapid-rotation missile body structure and a rotational speed design method, which comprises a body structure with a wedge-shaped block, specifically a body, a tail rudder and a wedge-shaped block. The body is an axisymmetric rotary body, comprising a head cone section and a cylindrical section. The tail rudder is located at the tail of the cylindrical section and is symmetrically distributed up and down and left and right. The wedge-shaped block is installed on the left side or the right side of the tail rudder, and the thicker end is located at the rudder tip. The rotational speed of the designed shape is determined by using the proposed rapid calculation method of rolling rotational speed, which comprises the following steps: 1. determining the rotational derivative of the shape of the aircraft without the wedge-shaped block by forced oscillation or free oscillation numerical method; 2. calculating the static rolling moment of the shape with the wedge-shaped block; and 3. determining the final rolling rotational speed of the missile. The method greatly improves the calculation efficiency of the rotational speed, and can guarantee high prediction accuracy at the same time. In combination with the layout design form of the wedge-shaped block added to the rudder surface, the method can be used for the detailed engineering design of the rolling rotational speed of the supersonic rotating missile.

Description

Technical Field

[0001] This invention belongs to the field of aircraft aerodynamic design and relates to a method for designing the structure and rotational speed of a rapidly rotating missile body. Background Technology

[0002] To maintain missile stability, facilitate control, and improve accuracy, small spinning missiles exhibit continuous spin motion around their longitudinal axis during flight. Traditional spinning missile speed design typically employs a pre-set control deflection method. When the required speed is small and control surface roll control efficiency is high, the pre-set control deflection angle is usually on the order of fractions. Assembly errors can significantly impact the actual speed, resulting in a loss of design accuracy. Furthermore, in the detailed engineering design of roll speed, the most effective method for predicting the speed is currently through coupled solution of the CFD-RBD control equations, releasing the roll direction degree of freedom for unsteady numerical simulation. However, this method is computationally intensive and time-consuming, leading to significant evaluation costs during iterative design processes. Summary of the Invention

[0003] The problem solved by this invention is to overcome the shortcomings of the prior art and provide a design method for the structure and rotation speed of a supersonic rotating missile body, aiming to reduce design deviations and calculation cycles, and provide technical support for the detailed engineering design of supersonic rotating missiles.

[0004] The technical solution adopted in this invention is:

[0005] This invention discloses a supersonic rotating missile body structure with wedge blocks, comprising: a missile body, tail fins, and wedge blocks; the missile body is an axisymmetric rotating body, including a nose cone section and a cylindrical section; several tail fins are located at the tail of the cylindrical section; the wedge blocks are wedge-shaped structures installed on one side of the tail fins, with the thicker end of the wedge structure located at the fin tip; a rapid roll speed calculation method is used to determine the missile body rotation speed, and the number and size of the wedge blocks are adjusted to make the missile body structure meet the roll speed requirements.

[0006] In the above-mentioned projectile structure, the projectile rotational speed is determined using a rapid calculation method. The number and size of the wedge blocks are adjusted to ensure the projectile structure meets the required rotational speed. Specifically:

[0007] Step 1: Based on the given flight altitude H and flight Mach number Ma, calculate the dynamic aerodynamic characteristics of the shape without the wedge block using forced oscillation or free oscillation numerical methods, and obtain the rotational dynamic derivative.

[0008] Step 2: Adjust the number, length, width, and thickness of the wedge blocks;

[0009] Step 3: Calculate the static rolling moment Cmx of the wedge-shaped block.

[0010] Step 4: Calculate the rolling speed of the wedge-shaped block.

[0011] Step 5: Compare the rolling speed of the wedge block with the design speed; if the relative deviation is less than 5%, the design is completed; otherwise, repeat steps 2-4.

[0012] In the above-mentioned projectile structure, the projectile length is 1000-5000 mm.

[0013] In the above-mentioned projectile structure, there are 2 to 8 tail fins, which are evenly distributed circumferentially along the tail section of the projectile column.

[0014] In the above-mentioned projectile structure, the chord length X of the tail rudder is 100-500mm, the span Z is 50mm-200mm, the leading edge radius R is 1mm-20mm, and the leading edge sweep angle λ is 30-70 degrees.

[0015] In the above-mentioned projectile structure, the number of wedge-shaped blocks is 1 to 8, and they are all installed on the left or right side of the tail rudder when viewed from the bottom of the projectile.

[0016] In the above-mentioned projectile structure, the length L of the wedge block is 10-200mm, the width W is 5-100mm, and the thickness D is 1.0-10.0mm.

[0017] In the above-mentioned projectile structure, the flight altitude H is 0 to 50 km, and the flight Mach number Ma is 1.5 to 10.

[0018] In the above-mentioned projectile structure, the adjustment of the number, length, width, and thickness of the wedge blocks specifically involves: if the calculated rolling speed of the wedge block shape is greater than the design speed, then the number, length, width, and thickness of the wedge blocks are reduced; conversely, the number, length, width, and thickness of the upper wedge blocks are increased.

[0019] This invention discloses a method for designing the rotational speed of a supersonic rotating missile, comprising:

[0020] Step S1: Design a projectile structure with wedge blocks, including: projectile body, tail rudder, and wedge blocks; the projectile body is an axisymmetric spun body, including a nose cone section and a cylindrical section; several tail rudders are located at the tail of the cylindrical section; the wedge blocks are wedge-shaped structures, installed on one side of the tail rudders, with the thicker end of the wedge structure located at the rudder tip;

[0021] Step S2: Based on the given flight altitude H and flight Mach number Ma, calculate the dynamic aerodynamic characteristics of the shape without the wedge block using forced oscillation or free oscillation numerical methods to obtain the rotational dynamic derivative.

[0022] Step S3: Adjust the number, length, width, and thickness of the wedge blocks;

[0023] Step S4: Calculate the static rolling moment Cmx of the wedge-shaped block.

[0024] Step S5: Calculate the rolling speed of the wedge-shaped block.

[0025] Step S6: Compare the rolling speed of the wedge block with the design speed; if the relative deviation is less than 5%, the design ends; otherwise, repeat steps S2-S5.

[0026] Compared with the prior art, the present invention has the following advantages:

[0027] (1) The present invention uses the method of installing wedge blocks to generate asymmetric rolling torque. By adjusting the number of wedge blocks and the three dimensions of length, width and thickness, the rolling torque can be precisely designed, while avoiding excessive assembly deviation.

[0028] (2) This invention utilizes the formula The calculation directly obtains the roll speed, and can quickly predict the speed based on only the initial dynamic derivative of the shape and the steady roll torque of the designed shape. This greatly increases the design efficiency, while the prediction accuracy is comparable to that of the free oscillation unsteady simulation method. Attached image description:

[0029] Figure 1 This is a schematic diagram of the aerodynamic layout of the present invention;

[0030] Figure 2 This is a schematic diagram showing the relative position of the wedge block of the present invention installed on the tail rudder;

[0031] Figure 3 This is a schematic diagram of the tail rudder dimensions of the present invention;

[0032] Figure 4 This is a schematic diagram of the dimensions of the wedge block of the present invention. Detailed Implementation

[0033] The working principle and process of the present invention will be further explained and described below with reference to the accompanying drawings.

[0034] This invention discloses a supersonic rotating missile body structure with wedge blocks, comprising: a missile body 1, tail fins 2, and wedge blocks 3; the missile body 1 is an axisymmetric rotating body, including a nose cone section and a cylindrical section; several tail fins 2 are located at the tail of the cylindrical section; the wedge blocks 3 are wedge-shaped structures installed on one side of the tail fins 2, with the thicker end of the wedge structure located at the fin tip; the missile body rotation speed is determined using a rapid roll speed calculation method, and the number and size of the wedge blocks 3 are adjusted to ensure the missile body structure meets the roll speed requirements. The missile body length is 1000–5000 mm. The number of tail fins 2 is 2–8, evenly distributed circumferentially along the tail of the cylindrical section of the missile body. The chord length X of the tail fins 2 is 100–500 mm, the span Z is 50 mm–200 mm, the leading edge radius R is 1 mm–20 mm, and the leading edge sweep angle λ is 30–70 degrees. The number of wedges ranges from 1 to 8, all mounted on the left or right side of the tail fin when viewed from the bottom of the missile body. The length L of wedge 3 is 10–200 mm, the width W is 5–100 mm, and the thickness D is 1.0–10.0 mm. The flight altitude H is 0–50 km, and the flight Mach number Ma is 1.5–10.

[0035] The projectile rotational speed is determined using a rapid calculation method. The number and size of the wedge blocks 3 are adjusted to ensure the projectile structure meets the required rotational speed. Specifically:

[0036] Step 1: Based on the given flight altitude H and flight Mach number Ma, calculate the dynamic aerodynamic characteristics of the shape without the wedge block using a forced oscillation or free oscillation numerical method to obtain the rotational dynamic derivative.

[0037] Step 2: Adjust the number, length, width, and thickness of the wedge blocks. Specifically, if the calculated rolling speed of the wedge block shape is greater than the design speed, reduce the number, length, width, or thickness of the wedge blocks; otherwise, increase the number, length, width, or thickness of the upper wedge blocks.

[0038] Step 3: Calculate the static rolling moment Cmx of the wedge-shaped block.

[0039] Step 4: Calculate the rolling speed of the wedge-shaped block.

[0040] Step 5: Compare the rolling speed of the wedge block with the design speed; if the relative deviation is less than 5%, the design is completed; otherwise, repeat steps 2-4.

[0041] This invention discloses a method for designing the rotational speed of a supersonic rotating missile, comprising:

[0042] Step S1: Design a projectile structure with wedge blocks, including: projectile body 1, tail rudder 2, and wedge block 3; the projectile body 1 is an axisymmetric spun body, including a nose cone section and a cylindrical section; several tail rudders 2 are located at the tail of the cylindrical section; the wedge block 3 is a wedge-shaped structure, installed on one side of the tail rudder 2, with the thicker end of the wedge structure located at the rudder tip.

[0043] Step S2: Based on the given flight altitude H and flight Mach number Ma, calculate the dynamic aerodynamic characteristics of the shape without the wedge block using forced oscillation or free oscillation numerical methods to obtain the rotational dynamic derivative.

[0044] Step S3: Adjust the number, length, width, and thickness of the wedge blocks;

[0045] Step S4: Calculate the static rolling moment Cmx of the wedge-shaped block.

[0046] Step S5: Calculate the rolling speed of the wedge-shaped block.

[0047] Step S6: Compare the rolling speed of the wedge block with the design speed; if the relative deviation is less than 5%, the design ends; otherwise, repeat steps S2-S5.

[0048] Example

[0049] A specific method for designing the rotational speed of a supersonic rotating missile in an example of this invention is as follows:

[0050] like Figure 1 As shown, an aerodynamic layout for a supersonic rotating missile includes a missile body 1, tail fins 2, and wedge-shaped blocks 3. The missile body is an axisymmetric rotating body, divided into a nose cone section and a cylindrical section along the flow direction. The nose cone section is 400 mm long, and the cylindrical section is 1800 mm long. Four tail fins are used, with an included angle of 90° between them. The tail fin chord length X is 252 mm, and the span Z is 90 mm. Figure 3 As shown.

[0051] The reference length for this shape is 2.2m, and the reference area is 0.025m². 2 The torque integral reference point is (1.16, 0, 0). The angle of attack and sideslip angle used for comparison and analysis are 0° and 0°, respectively, with a corresponding flight altitude H of 5km and Mach numbers Ma of 3, 4, and 5. Based on practical application requirements, a roll speed of -3 r / s is required under Mach number Ma = 4.

[0052] The rolling derivatives of the initial shape under three Mach numbers were calculated using the forced oscillation method, as shown in the table below.

[0053] A rudder wedge block was designed using the method described in this invention, such as... Figure 2As shown, a wedge block is installed on the tail rudder, attached to the left side of the rudder surface. The size of the wedge block was determined based on the additional torque requirements of its shape. Figure 4 As shown in the enlarged view, the length L is 60mm, the width W is 10mm, and the thickness D is 3.5mm.

[0054] The roll speed was predicted using the method of this invention, and the results were compared with those of unsteady numerical simulation methods. As shown in the table below, the calculated speed deviation using the method of this invention is less than 5% compared with the unsteady simulation method, and the calculation deviation tends to decrease as the incoming flow Mach number increases, which can meet the accuracy requirements of engineering design.

[0055]

[0056] The above embodiments are merely explanations of the present invention and should not be construed as limiting the present invention. Therefore, any implementation methods similar to the present invention or implementation methods used in other similar structures but with similar concepts to the present invention are within the protection scope of the present invention.

[0057] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the protection scope of the present invention.

[0058] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A supersonic rotating missile body structure, characterized in that, include: The projectile (1), tail rudder (2), and wedge block (3) are as follows: The projectile (1) is an axisymmetric spiral body, including a nose cone section and a cylindrical section; Several tail rudders (2) are located at the tail of the cylindrical section; The wedge block (3) is a wedge-shaped structure installed on one side of the tail rudder (2), with the thicker end of the wedge structure located at the rudder tip; The projectile speed is determined by a rapid calculation method of roll speed, and the projectile structure meets the roll speed requirements by adjusting the number and size of the wedge blocks (3); The projectile rotational speed is determined by a rapid calculation method for the roll speed. The number and size of the wedge blocks (3) are adjusted to make the projectile structure meet the roll speed requirements. Specifically: Step (1) Based on the given flight altitude H and flight Mach number Ma, calculate the dynamic aerodynamic characteristics of the shape without the wedge block using the forced oscillation or free oscillation numerical method, and obtain the rotational dynamic derivative. ; Step (2) Adjust the number, length, width, and thickness of the wedges; Step (3) Calculate the static rolling moment of the wedge block shape. ; Step (4) Calculate the rolling speed of the wedge-shaped block. ; Step (5) compare the rolling speed of the wedge-shaped block with the design speed; if the relative deviation between the two is less than 5%, the design is terminated. Otherwise, repeat steps (2)-(4).

2. The supersonic rotating missile body structure according to claim 1, characterized in that: The projectile has a length of 1000~5000mm.

3. The supersonic rotating missile body structure according to claim 1, characterized in that: The tail rudder (2) consists of 2 to 8 pieces, which are evenly distributed around the tail of the projectile column.

4. The supersonic rotating missile body structure according to claim 1, characterized in that: The tail rudder (2) has a chord length X of 100~500mm, a span Z of 50mm~200mm, a leading edge radius R of 1mm~20mm, and a leading edge sweep angle λ of 30~70 degrees.

5. The supersonic rotating missile body structure according to claim 1, characterized in that: The number of wedge-shaped blocks is 1 to 8, and they are all installed on the left or right side of the tail rudder when viewed from the bottom of the projectile.

6. The supersonic rotating missile body structure according to claim 1, characterized in that: The wedge block (3) has a length L of 10-200 mm, a width W of 5-100 mm, and a thickness D of 1.0-10.0 mm.

7. The supersonic rotating missile body structure according to claim 1, characterized in that: The flight altitude H is 0~50km, and the flight Mach number Ma is 1.5~10.

8. The supersonic rotating missile body structure according to claim 1, characterized in that: The adjustment of the number, length, width, and thickness of the wedge blocks is specifically as follows: if the calculated rolling speed of the wedge block shape is greater than the design speed, then the number, length, width, and thickness of the wedge blocks are reduced; otherwise, the number, length, width, and thickness of the upper wedge blocks are increased.

9. A method for designing the rotational speed of a supersonic rotating missile, characterized in that, include: Step S1: Design a projectile structure with wedge blocks, including: projectile body (1), tail rudder (2), and wedge block (3); the projectile body (1) is an axisymmetric spiral body, including a head cone section and a cylindrical section; several tail rudders (2) are located at the tail of the cylindrical section; the wedge block (3) is a wedge-shaped structure, installed on one side of the tail rudder (2), and the thicker end of the wedge structure is located at the rudder tip; Step S2: Based on the given flight altitude H and flight Mach number Ma, calculate the dynamic aerodynamic characteristics of the shape without the wedge block using forced oscillation or free oscillation numerical methods to obtain the rotational dynamic derivative. ; Step S3: Adjust the number, length, width, and thickness of the wedge blocks; Step S4: Calculate the static rolling moment of the wedge-shaped block. ; Step S5: Calculate the rolling speed of the wedge-shaped block. ; Step S6: Compare the rolling speed of the wedge-shaped block with the design speed; if the relative deviation between the two is less than 5%, the design is completed. Otherwise, repeat steps S2-S5.

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